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2011-18-10: We are superseding an existing airworthiness directive (AD) for the products listed above. The existing AD currently requires reviewing the airplane maintenance records to determine whether an engine has been removed from the airplane since the airplane was manufactured. For airplanes on which an engine has been removed, the existing AD also requires an inspection of the aft engine mount to determine if the center link assembly is correctly installed, and follow-on actions if necessary. This new AD expands the applicability to include airplanes on which the engine has not been previously removed, and Model 737-900ER airplanes. This AD was prompted by reports indicating that operators found that the center link assembly for the aft engine mount was reversed on several airplanes that had not had an engine removed since delivery. We are issuing this AD to prevent increased structural loads on the aft engine mount, which could result in failure of the aft engine mount and consequent separation of the engine from the airplane.
48-07-03: 48-07-03\tDOUGLAS: Applies to DC-6 Serial Numbers 42854 Through 42896; 43000 Through 43024; 43035 through 43053; 43055 Through 43064; 43103 Through 43119; 43129 and 43132 (Note: Some of the Above Airplanes May Have Had Part of the Changes Installed Before Delivery From the Factory.) \n\n\tCompliance required by September 15, 1948. \n\n\tTo provide safer and more satisfactory operation of all the doors, the following reworks must be accomplished: \n\n\t(1)\tInstall new latch bolts on all emergency exit doors, main passenger door, crew door, heater compartment door, and belly cargo compartment doors, to incorporate a notch which allows slow depressurization before the door can be fully opened in the event the handles are inadvertently turned toward the "OPEN" position while the cabin is pressurized. \n\n\t(2)\tRework the operating and locking mechanisms of the passenger, crew, and emergency exit doors, to increase their strength and prevent malfunctioning. \n\n\t(3)\tInstall visual inspectionplugs in the passenger, crew, and emergency exit doors to allow individual inspection of each lock bolt to determine if it is properly locked. \n\n\t(4)\tInstall an assist handle above the main cabin door handle to prevent accidental grabbing of the inside door handle. (NOTE: Even in cases where the door handles have been changed so that the handle points downward when the door is closed and locked, it will still be necessary to install the assist handles.)
2022-02-17: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH (AHD) Model MBB-BK 117 C-2, MBB-BK 117 D-2, and MBB-BK 117 D-3 helicopters. This AD was prompted by reports of engine flame out following prolonged operations in falling snow on helicopters with an inlet barrier filter (IBF) system installed. This AD requires revising the existing Rotorcraft Flight Manual (RFM) for your helicopter, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
49-04-01: 49-04-01 BEECH: Applies to Model 35 Serial Numbers D-1 to D-1300, Except D-69, D- 315, D-356, D-754, D-827, D-1117, D-1120, D-1201, D-1251, D-1274, D-1278, D-1285, D-1289, D-1290, D-1291, D-1293, D-1295, D-1296, D-1298 and D-1299. To be accomplished at next 100-hour inspection but not later than May 1, 1949. Remove aileron control wheel drive chain assembly from the control arm of the specified aircraft, which have not had the chain replaced by Beech facilities, and visually inspect the pin through each link for proper up-set heads on each end of the pin. Chains having end ferrules dyed green have been replaced by Beech facilities and need not be inspected. (Beech Service Bulletin No. 35-8, revised January 3, 1949, covers this same subject.)
93-17-02: 93-17-02 BOEING: Amendment 39-8672. Docket 93-NM-05-AD. Supersedes AD 91-20-11, Amendment 39-8045. \n\n\tApplicability: Model 737-300, -400, and -500 series airplanes, line positions through 2428, inclusive; and Model 737-200 series airplanes, equipped with DC powered fuel tank float switches; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously.\n \n\tTo prevent failure of the wing main tank float switch electrical conduits and subsequent fuel leakage resulting in an engine tail pipe fire, accomplish the following: \n\n\t(a)\tFor airplanes listed in Boeing Service Letter 737-SL-28-36, dated November 30, 1990: Within 90 days after November 7, 1991 (the effective date of AD 91-20-11, Amendment 39-8045), and thereafter at intervals not to exceed 1,500 flight hours, perform an inspection of the wing main tank float switch electrical conduits for fuel leakage and condensation build-up, in accordance with Boeing Service Letter 737-SL-28-36, dated November 30, 1990. If evidence of fuel leakage and/or water condensation is found while performing the initial or repetitive inspections, prior to further flight, purge and install a new vapor seal assembly in accordance with the Boeing service letter. \n\n\tNOTE 1: The installation of a new vapor seal assembly does not terminate the requirement for the 1,500 flight hour repetitive inspection. \n\n\t(b)\tFor airplanes listed in Boeing Service Letter 737-SL-28-42, dated December 15, 1992, that are not subject to paragraph (a) of this AD: Within 90 days after the effective date of this AD, and thereafter at intervals not to exceed 1,500 flight hours, perform an inspection of the wing main tank float switch electrical conduits for fuel leakage and condensation build-up, in accordance with Boeing Service Letter 737-SL-28-36, dated November 30, 1990. If evidence of fuel leakage and/or water condensation is found while performing the initial or repetitive inspections, prior to further flight, purge and install a new vapor seal assembly in accordance with the Boeing service letter. \n\n\tNOTE 2: The installation of a new vapor seal assembly does not terminate the requirement for the 1,500 flight hour repetitive inspection. \n\n\t(c)\tWithin 3 years after the effective date of this AD, install grease in the interior of the wing main tank float switch electrical conduits in accordance with Boeing Service Letter 737-SL-28-42, dated December 15, 1992, or 737-SL-28-42-A, dated July 15, 1993. Installation of grease in the conduits constitutes terminating action for the inspections required by paragraphs (a) and (b) of this AD. \n\n\t(d)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(e)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. \n\n\t(f)\tThe inspections shall be done in accordance with Boeing Service Letter 737-SL-28-36, dated November 30, 1990. The installation shall be done in accordance with Boeing Service Letter 737-SL-28-42, dated December 15, 1992, or Boeing Service Letter 737-SL-28-42-A, dated July 15, 1993. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport AirplaneDirectorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. \n\n\t(g)\tThis amendment becomes effective on November 24, 1993.
2012-18-02: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 and AB412 EP helicopters with certain hoist hook assemblies (hook) installed. This AD requires inspecting the hook for correct assembly of the nut and body. This AD is prompted by a report that a hook separated from the cable of a helicopter. These actions are intended to prevent detachment of the hook from the helicopter and subsequent loss of an external load, possibly resulting in personal injury.
2011-20-07: We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires replacement of the power control relays in the P91 and P92 power distribution panels for the fuel boost and override pumps with new, improved relays having a ground fault interrupter (GFI) feature, or installation and maintenance of universal fault interrupters (UFIs) using a certain supplemental type certificate. This new AD continues to require the actions of the existing AD and also specifies which relays may be replaced by GFIs or UFIs. This AD was prompted by a need to clarify which relays may be replaced by installation of UFIs. We are issuing this AD to prevent pump housing burn-through due to electrical arcing, which could create a potential ignition source inside a fuel tank. This condition, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
93-08-01: 93-08-01 FOKKER: Amendment 39-8548. Docket 92-NM-191-AD. Applicability: Model F27 series airplanes in post-Fokker Service Bulletin F27/57-9 configuration; serial numbers 10115, 10126 through 10684, inclusive; 10686, 10687, and 10689 through 10692, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural capability of the wings, accomplish the following: (a) Inspect the lower skin at the runout of stringers 2 and 10 near wing stations 6490, 5330, and 6100 to detect cracks, in accordance with Fokker Service Bulletin F27/57-69, dated April 6, 1992, at the time specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD, as applicable: (1) For airplanes that have accumulated less than 20,000 total landings as of the effective date of this AD: Prior to the accumulation of 20,000 total landings, or within 1 year after the effective date of this AD, whichever occurs later. (2) For airplanes that have accumulated 20,000 or more total landings, but less than 30,000 total landings, as of the effective date of this AD: Prior to the accumulation of 30,000 total landings, or within 5 months after the effective date of this AD, whichever occurs later. (3) For airplanes that have accumulated 30,000 or more total landings as of the effective date of this AD: Within 2 months after the effective date of this AD. (b) If any crack is found as a result of the inspection required by paragraph (a) of this AD, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (c) Within 10 days after accomplishing the inspection required by paragraph (a) of this AD, report positive findings of cracks to Fokker, in accordance with Fokker Service Bulletin F27/57-69, dated April 6, 1992. Information collection requirements contained in this regulation have been approvedby the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The inspection and report shall be donein accordance with Fokker Service Bulletin F27/57-69, dated April 6, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on May 27, 1993.
48-12-01: 48-12-01 DOUGLAS: Applies to All C-54 and DC-4 Aircraft As Specified by Civil Air Regulations Amendments 41-3, 42-2, and 61-2. \n\n\tTo be accomplished not later than the dates specified in the above amendments as revised by special Civil Air Regulations Serial Nos. 385, 390, 390A, 390B and any subsequent regulations affecting these compliance dates. \n\n\tAll air carrier aircraft must be modified to comply with the fire prevention requirements as outlined in CAR Amendments 41-3, 42-2, and 61-2. The modifications outlined in the following listed Douglas Service Bulletins and AD 47-42-03 are required for compliance with these amendments. Other modifications shown to be equivalent to those covered by the Service Bulletins will also be acceptable. \n\n\tService Bulletin No. 62, Install Smoke Detector in Belly Baggage Compartment; Service Bulletin No. 66, Engine Section Piping and Fitting Revision; Service Bulletin No. 69, Installation of Enclosed Waste Container in Lavatory. \n\n\tIn addition to the above it will be necessary to ascertain that all interior materials and finishes comply with the applicable sections of CAR 4b. Safety Regulation Release 259 outlines acceptable procedures for complying with these particular requirements.
98-12-30: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-12-30 which was sent previously to all known U.S. owners and operators of McDonnell Douglas Helicopter Systems (MDHS) Model MD-900 helicopters by individual letters. This AD requires inspecting the main rotor upper hub assembly (hub assembly) for cracks, and if a crack is found, replacing the hub assembly. The AD also requires verifying attachment nut torque values and a repetitive inspection at intervals not to exceed 150 hours time-in-service. This amendment is prompted by the discovery of cracks in 6 main rotor upper hub assemblies. This condition, if not corrected, could result in failure of the hub assembly, loss of drive to the main rotor, and subsequent loss of control of the helicopter.